Rocket propelled reconnaissance vehicle



Nov. 24, 1964 .1. D. FINLEY ROCKET PROPELLED RECONNAISSANCE VEHICLE I5Sheets-Sheet 1 Original Filed July 22, 1960 [NV ENT OR JACK D. FINLEYATTORNEY Nov. 24, 1964 J. D. FINLEY ROCKX IT PROPELLED RECONNAISSANCEVEHICLE Original Filed July 22, 1960 3 Sheets-Sheet 2 KOPOE 022mm nzE.mama mm mm INVENTOR JACK D. FINLEY ATTORNEY Nov. 24, 1964 J. D. FINLEY3,158,100

ROCKET PROPELLED RECONNAISSANCE VEHICLE Original Filed July 22, 1960 3Sheets-Sheet 3 mama 0 mokoz A|H|\\ uzaim m V n l .2 mm M v 4H =5 #25532km mm n=E 3255M: mm

INVENTOR JACK D. FINLEY ATTORNEY Patented Nov. 24*, 1964 3,158,190ROCKET PROPELLED REQDNNAISEANCE VEHTCLE Jack D. Finley, Dayton, Ohio,assignor, by mesne assignments, to Data Corporation, Dayton, Ohio, atcorporation of Ohio Continuation of application Ser. No. 44,613, .luiy22, 1960. This application Mar. 4, 1963, Ser. No. 263,381 17 Claims.(Cl. Mil-A9) This invention relates to aerial reconnaissance vehiclesgenerally and more particularly to an improved rocket propelledreconnaissance vehicle for gathering aerial intelligence information. Asdisclosed herein, the invention constitutes a continuation of myco-pending application entitled Rocket Propelled Reconnaissance Vehicle,Serial No. 44,613, filed July 22, 1960.

In all phases of military operations, it is imperative that accurateinformation be obtained relative to conditions within an enemy territoryby reconnaissance techniques. These reconnaissance techniques includemilitary ground and sea reconnaissance, battle field surveillance,weather data collection, boundary penetration, collection of data duringpenetration of atomic clouds, and many other analogous areas whereremote intelligence gathering is desired.

Present reconnaissance techniques include the use of aerial dynamicvehicles of the piloted variety and also pilotless aircraft or drones.These vehicles are not amenable to rapid and simple deployment and arenot suitable for prolonged high altitude operation. Also such vehiclesrequire a degree of support which is unacceptable for many applications.

The piloted reconnaissance aircraft presently in use usually consist ofhigh speed, unarmed aircraft, and an extreme degree of risk isexperienced by the crew of such aircraft while gathering informationover enemy targets.

The drone or pilotless aircraft, which are often utilized to replace thepiloted reconnaissance aircraft, are equipped with control systems,guidance equipment, and aerial dynamic controls which are used toprovide a controlled turn-about at the target and a controlled flightback to a desired point within friendly territory. The guidance equimentnecessary to perform a control turn over target and a return flight to afriendly base is extremely expensive to build and is very complex innature and therefore subject to a large degree of malfunction.

The primary object of this invention is to provide a rocket propelledreconnaissance vehicle capable of returning a payload from a preselectedtarget area along a ballistic trajectory.

Another object of this invention is to provide a rocket propelledreconnaissance vehicle capable of returning a payload from apre-selected target area along a ballistic trajectory by means of arearward firing rocket propelled recovery vehicle. l

A further object of this invention is to provide a rocket propelledreconnaissance vehicle of the two stage variety which includes arearwardly firing rocket propelled recovery vehicle capable of beinglaunched from within a primary delivery stage vehicle over a targetarea.

Another object of this invention is to provide a rocket propelledreconnaissance vehicle which may be launched from the ground, fromground vehicles, from aircraft, or from ships and submarines.

A further object of this invention is to provide a rocket propelledreconnaissance vehicle of economic size and weight with resultingfreedom of movement and speed of deployment.

A still further object of this invention is to provide a rocketpropelled reconnaissance vehicle of simple design which may beeconomically produced for use in high altitude reconnaissance.

With the foregoing and other objects in view, the invention resides inthe following specification and appended claims, certain embodiments anddetails of construction of which are illustrated in the accompanyingdrawings in which:

FIGURE 1 is a cut-away view in side elevation of the inventionillustrating the relationship of the delivery and recovery stages,

FIGURE 2. is an end view illustrating the aft portion of the inventionof FIGURE 1,

FIGURE 3 is a sectional view in side elevation showing the recoverystage of the invention of FIGURE 1,

FIGURE 4 is an end view illustrating the aft portion of the recoverystage of FIGURE 3,

FIGURE 5 is an exploded view illustrating the fin locking mechanism ofthe recovery stage of FIGURE 3,

FIGURE 6 is a diagrammatic layout illustrating the activating mechanismfor the fin locking; mechanism of FTGURE 5; and

FIGURE 7 is a block diagram showing the control system for the inventionof FIGURE 1.

Basically, the rocket propelled reconnaissance vehicle of the presentinvention includes a two-stage rocket propelled vehicle consisting of adelivery stage missile and a recovery stage missile. The recovery stagemissile is contained within the delivery stage missile, and is carriedalong a ballistic trajectory to a target by the delivery stage. When apro-selected target area is reached, intelligence information isgathered by equipment within the recovery stage and the recovery stagemissile is then rearwardly launched from within the delivery stage andreturns over a ballistic trajectory to the original launching area. Therocket motors utilized for the propulsion of each stage of thereconnaissance vehicle are conventional solid propulsion motors withsufiicient total impulse to allow the vehicle stages to arrive over andreturn from the pre-selected target area. The delivery and recoverystages include high fineness ratio rockets and the propeilant fractionis the variable range control for the individual rocket stages, althoughother active control means could be utilized for the improvement oftargeting.

Launching of the reconnaissance vehicle is to be accomplished from arail launcher, and targeting can be computed by the. use of tablessimilar to the conventional artillery data used for the targeting ofguns, and from local meteorological data. The variables at the launcherwill be the azimuth and elevation of the launcher, and the wind andtarget information may be: translated into these two variables byreference to appropriate tables. Thus, it may be seen that the presentreconnaissance vehicle may be launched as a purely ballistic missilewithout the requirement of expensive electronic control guidancemechanisms.

Referring to FIGURE 1, the rocket propelled reconnaissance vehicleindicated generally at 10 includes a delivery stage 11 which carries arecovery stage 12. The delivery stage 11 includes a body section 13which is substantially in the form of an open cylinder. Body 13 isequipped with four peripherally spaced U-shaped slides 14 extendinglongitudinally along the inner wall thereof. Mounted externally aboutthe aft portion of the cylindrical body 13 are propulsion rocket engines15 and stabilizing fins 16 (FIGURE 2). The rocket engines 15 for thedelivery stage 11 are externally mounted in order to afford a clearinternal passageway through the cylindrical body 13. The forward end ofthe cylindrical body 13 is provided with an aerodynamic cap 17 whichprotects thepayload Within the delivery stage 11 and provides a methodfor reducing aerodynamic drag during the delivery flight. ArrangedWithin the body 13 of 'the delivery stage.

the delivery stage 11 are a number of compartments 18 I which contain asequencing control mechanism for activating the various phases ofoperation of the reconnaissance vehicle 10. These compartments are fewin num her and the components contained within each compartment areexpendable. The compartments 18 are arranged so as not to interfere withthe launching of the recovery stage 12.

. Referring to FIGURES 3 and 4, it will be noted that the recovery stage12 is similar in external configuration to the delivery stage 1-1. Therecovery stage includes a cylindrical body 19 which is dimensioned tofit inside the open cylindrical body 13 of the delivery stage 11. .Theforward or nose .portion of the body 19 is provided with a jettisonableaerodynamic bearing or cap 20 which provides a compartment 55 for arecovery parachute, .here shown in dotted lines. Rocket motors 21 aremounted externally of the aft. portion of the body 19 to allow for theinstallation of a payload chamber 22 in the internal tail portion of therecovery stage 12. Any'desired intelligence sensor for providing therequired recon- :naissance information may be mounted within the pay-.load chamber 22. The central portion of the body 19 is provided with amechanism compartment 23 where the .control mechanism for the recoverystage is mounted.

Extending longitudinally along the external portion :of the body 19 ofthe return stage 12 are four T-shaped slides 24 which mount laterallyprojecting stabilizing fins 25. The recovery stage 12 is mounted withinthe delivery stage 11 by inserting the fins 25 in the U-shaped,

slides 14 so that the U-shaped slides may act as a launching ramp forthe recovery stage. The recovery "stage 12 is inserted into the deliverystage 11 with the aerodynamic cap toward the tail section of the de--livery stage, since the ejection and the return/of the recovery-stageis to be in this direction. As the recovery stage 12 is to befired in arearward direction with respect to the initial direction of-the travelthrough the air mass, means must be provided for stabilizing therecovery stage. 'This is accomplished by physically'moving the fins inthe slides 24 to a position near the aerodynamic cap 20 prior to theinstallation of the recovery stage within 7 When the recovery stage 12is launched, the position of the fins '25 will determine the position ofthe'center of pressure. The center of pressure will be toward theaerodynamic cap 20 with respect to the center of gravity'when therecovery stage is so situated that the ambient airflow is toward thepayload. At a predetermined period of time after'firing when the 'thrustof the. rockets 21 has diminished the air speed to Zero in the directiontaken by the delivery stage 11, and a positive air speed has beenattained in the direction of the return trip, the fins 25 will be movedrearwardly in the slidesj24 as shown in FIGURE 3, so that the center ofpressure will be shifted to a position behind the center of gravity withrespect to the direction of travel, and -the missile will thus'bestable. 1

Referring now to FIGURES 5 and 6, the afore-de- 'scribed movement of thefins 25 within the slides 24 is controlled by spring pressed locks 26and 27. The locks 26 and 27 are situated within the slides 24 andcooperate with'a notch 28 which is provided in the lower surface of thefin25. When a fin 25 is in the forward or firing position, the lock 26is engaged within the notch 28 to securelyhold the fin in this position.At the proper time after the firing of the return stage 12, the lock 26is retracted by means of a lanyard unlocking mechanism 29, and fin 25 isforced rearwardly in the slide 24 by inertia -and aerodynamic drag untilthe lock 27 engages in the islot 28. The lock 27 is designed to offervirtually no resistance to fin 25 as it passes along the body 19 in arearward direction. Once the lock 27-is engaged in the "slot 28, highresistance is offered to any attempt byfin dynamic air pressure ambientat the cap. 'of the lanyard pull 45 causes the lanyard 47 to .free thelock 26 is operated by means of a mechanical control unit 30 illustratedin FIGURE 6. It is obvious that any suitable control unit which wouldact to release the forward lock 26 at a set time after the firing of thereturn stage 12 when the return stage had reached a predetermined posi-'tive air speed could be utilized. 'The control mechanism 34) of FIGURE 6includes an air speed sensing propeller 31 which drives a one way clutch-32. Clutch 32 is only sensitive to the direction of turn of thepropeller 31 which indicates travel through the air in the direction ofthe aerodynamic cap 24?. The clutch 32 drives a screw drive The controlsystem and operation of the twostage rocket propelled reconnaissancevehicle of the present invention may be best understood by referring toFIG- URE 7 which provides an illustration of a mechanical control unit36 for the delivery stage 11 and a mechanical control unit 37 for therecovery stage 12. Upon the launching of the reconnaissance vehicle 10,a lock-out timer 33 is activated. The timer .33 maybe any timing unit ofcommon mechanical designwhich may be set to activate a mechanical trip39, which has been previously locked out by the timer, a short time,'for example approximately seconds, after. the launching. The deliverystage 12 will continue along a ballistic trajectory until it begins adescent in the vicinity of the target area. When the delivery stagedescends to a predetermined altitude, which will be designated as h 1,a. bare bellows 40 will sense the altitude 711 and trigger the mechanical trip 39 to allow it to release a spring motor drive 41. Thespring motor'drive 41 is coupled by suitable mechanical or electricalmeans to a cam actuated switch 42 which, when activated by the springmotor 41, looks in the closed position. This switch 42-is electricallyconnected to a battery 43 and also to the reconnaissance equipment powerinput in the payload chamber 22 of the return stage 12. Activation ofthe switch 42 causes power to be provided to the reconnaissanceequipment in the' payload chamber 22, so that the equipment may begin togather target information. The spr ng motor drive 4-1 is alsomechanically coupled to a pair of lanyard pull mechanisms 44 and 45,which consist of drums designed to wind up lanyard cables 46 and 47. Thelanyard pull .44 is coupled to the release mechanism of the aerodynamiccap 17 on the delivery stage 12, and the tensioning of the lanyard 46retracts .a locking pin, such as lock 26 shown in FIG. 5; permitting thecap 17 to be ejected by the some lower altitude designated at [12, themechanical trip 39 under the control of the bellows 46 will activate aspring loaded switch 48 which connects a battery 49' to igniters carriedby the rockets 21 of the recovery-stage 12. At this point the rockets ofthe recovery stage fire,

causing the stage to leave the delivery stage and proceed in a directionoppositeto the direction of travel of the delivery stage. The recoverystage 12 will be stabilized by the stabilizing tins 25 in the mannerpreviously described, and will continue on a return ballistic trajectorytoward the original launching site until it begins a descent over thelaunching site. When the recovery stage descends to an-altitudedesignated at h3, which is small in comparison to the previousaltitudes, I11 and k2, the conuolling mechanism 37 within the recoverystage 12 will be actuated by a baro bellows 50. Baro bellows 50 operatesa mechanical trip 51 which in turn releases a spring motor,drive 52.Spring motor drive 52'drives a lanyard pull 53 to tension a lanyard 54whichis at- I 'tached'to the release mechanism of the aerodynamic capThe rotation h 26 of the recovery stage 12. Tensioning of the lanyard 54will retract a locking pin, such as lock 26 shown in FIG. causing thejettisoning of the aerodynamic cap it) and allowing a recovery parachuteto be ejected to one side to lower the stage with the payload to theground.

In some instances it might be desirable to decrease the speed of thereconnaissance vehicle it prior to the firing of the recovery stage 12.This may be done when the vehicle reaches the altitude hi by techniquessimilar to those employed for this purpose in other aerial vehicles. Thefirst method may be by the use of drag modulation in which the effectivedrag of the vehicle is increased by the extension of dive brakesactivated from the spring motor 41. The second method would be by thefiring of retro-rockets carried externally of the vehicle by means ofthe switch 42. Either method is feasible and has been successfullyemployed for other aerial purposes.

It will be readily apparent to those skilled in the art that the presentinvention provides a novel two-stage rocket propelled reconnaissancevehicle which is designed to deliver an intelligence gathering payloadto a point in space over a preselected target area and to return thepayload to an original launching area. The arrangement and types ofcomponents utilized within this invention may be subject to numerousmodifications well within the purview of this inventor who intends onlyto be limited to a liberal interpretation of the specification andappended claims.

I claim:

1. An aerial reconnaissance vehicle for gathering information over adesignated target area and returning said information to the area of aninitial launching site, comprising, a delivery stage racket including ahollow body section, a nose section, and a tail section, mounting meanssecured within said hollow body section, a recovery stage rocket havinga nose section and a tail section, said recovery stage rocket beingreversely mounted within said hollow body section by said mountingmeans, whereby the nose section of said recovery stage rocket ispositioned adjacent the tail section of said delivery stage rocket,information gathering means carried by said recovery stage rocket,altitude responsive control means carried by said vehicle for activatingsaid information gathering means when the vehicle reaches apredetermined first altitude over said target area, and altituderesponsive launching control means mounted within said vehicle to causethe launching of said recovery stage rocket from the tail section ofsaid delivery stage rocket subsequent to the activation of saidinformation gathering means when said vehicle reaches a secondpredetermined altitude over said target area, said recovery stage rocketbeing capable of returning said information gathering means to the areaof said initial launching siteupon detachment from said delivery stagerocket.

2. The aerial reconnaissance vehicle of claim 1 wherein said altituderesponsive control means for said information gathering means includesan altitude sensing means constructed to operate at a predeterminedaltitude, motor means connected to be actuated upon the operation ofsaid altitude sensing means, a power source coupled to provide power tosaid information gathering means, and switch means connected betweensaid power source and said information gathering means to selectivelycontrol the provision of power to said information gathering means, saidswitch means being connected to said motor means, whereby said switch isactuated to provide power to said reconnaissance means upon theactuation of said motor means.

3. The aerial reconnaissance vehicle of claim 2 wherein said altituderesponsive launching control means includes means connected to beoperated by the altitude responsive control means for said informationgathering means to free said second stage rocket for launching withinsaid mounting means, a second altitude sensing means constructed tooperate at a second predetermined altitude,

and means controlled by said second altitude sensing means to connectsaid power supply to said second stage rocket, whereby said second stagerocket is furnished with power to initiate the launching thereof fromwithin said first stage rocket.

4, An aerial reconnaissance vehicle for gathering in formation over adesignated target area and returning said information to the target areaof an initial launching site, comprising, a delivery stage rocketincluding a hollow body section, a nose section, and a tail section,mounting means secured within said hollow body section, a recovery stagerocket having a nose section and a tail section reversely mounted withinsaid hollow body section by said mounting means, whereby the nosesection of said recovery stage rocket is positioned adjacent the tailsection of said delivery stage rocket, said recovery stage rocketincluding laterally extending stabilizing means capable of longitudinalmovement along the body of said recovery stage rocket from a forwardlocking position to a rearward locking position, and stabilizationcontrol means carried by said recovery stage rocket to initiate thelongitudinal movement of said stabilizing means, information gatheringmeans mounted within said recovery stage rocket, altitude responsivecontrol means mounted within said vehicle for activating saidinformation gathering means when the vehicle reaches a firstpredetermined altitude over a tar et area, and altitude responsivelaunching control means mounted within said vehicle to cause thelaunching of said recovery stage rocket from the tail section or" saiddelivery stage rocket when the vehicle reaches a second predeterminedaltitude over said target area, said recovery stage rocket being capableof returning said infori ation gathering means to the area of saidinitial launching site upon detachment from said delivery stage rocket.

5. The aerial reconnaissance vehicle of claim 4 in which saidstabilization control means for said longitudinally moving stabilizingmeans includes locking means to selectively lock said stabilizing meansin either a forward or a rearward locking position along the body ofsaid recovery stage rocket, air speed responsive means adapted to becomeoperable when said recovery stage rocket reaches a predetermined forwardair speed after the launching from said delivery stage rocket, motormeans coupled to said air speed responsive means to be activatedthereby, a lock actuation means connected between said motor means andsaid locking means, said lock actuation means being actuated by saidmotor means to release said stabilizing means for longitudinal movementalong the body of said recovery stage rocket, the movement of saidstabilizing means acting to shift the center of pressure of saidrecovery stage rocket to cause flight stabilization thereof afterdetachment from said delivery stage rocket.

6. An aerial reconnaissance vehicle for gathering information over adesignated target area and returning said information to the area of aninitial launching site, comprising, a delivery stage rocket including anose section and a tail section, a recovery stage rocket reverselymounted within said delivery stage rocket, information gathering meanscarried by said recovery stage rocket, means carried by said vehicle foractivating said information gathering means when the vehicle reaches apredetermined position over said target area, launching control meansmounted within said vehicle to cause the launching of said recoverystage rocket from the tail section of said delivery stage rocketsubsequent to the activation of said information gathering means,variable stabilizing means including laterally extending fin membersmounted exteriorly of said recovery stage rocket and capable oflongitudinal movement from a forward to a rearward loclo ing positionalong the body of said recovery stage rocket, and air speed responsivecontrol means carried'by said recovery stage rocket, said control meansbeing responsive to the positive air speedof said recovery stage rocketsubsequent to the detachment thereof from said delivery stage rocket andoperatively connected to said stabilizing fin members to initiate thelongitudinal movement of said stabilizingfin members from the. forwardto the rearward locking position to cause the center or" pressure to lowbody section, an aerodynamic cap mounted upon one end of said bodysection, stabilizing fins and rocket propulsion means mounted externallyat tlie opposite end of said body section, and a plurality ofperipherally spaced :slide units extending longitudinally along theinner sur- "faces of said body section, a recovery stage rocket having ajettisonable aerodynamic cap mounted upon one end thereof andstabilizing fins and rocket propulsion means -mounted externally at theopposite end thereof, said recovery stage rocket being reversely mountedWithin the body of said delivery stage rocket with the aerodynamic capthereof adjacent the stabilizing fins'of said delivery stage rocket bythe insertion of the stabilizing fins of said recovery stage rocket intothe peripherally spaced slide units within said recovery stage rocket,information gath- "ering means' carried by said recovery stage rocket,pressure sensitive control means mounted within said vehicle toinitiate'the activation of said information gathering means when saidvehicle reaches a predetermined altitude above the target area, andlaunching control means carcomprising, a delivery stage rocket includinga nose section and rocket propulsion means, a recovery stage rocketincluding a nose section incorporated Within the body of said deliverystage rocket and detachably secured to said delivery stage rocket so asto be reversely mounted rela tive to the direction of travel of saiddelivery stage rocket, whereby the-nose section of said recovery stageracket is reversely positioned relative to the nose section of saiddelivery stage rocket, said recovery stage rocket having rocketpropulsion means and laterally extending fin members secured thereto,said fin members being mounted exteriorly of said recovery stage rocketand being capable of longitudinal movement along the body thereof,infor- "mation gathering means carriedby said recovery stage rocket,first control means carried by said vehicle, said first control meansoperating to initiate the information 1 gathering cycle of saidinformation gathering means and to cause the ejection of the nosesection of said delivery stage rocket at a first point over said targetarea, second control means carried by said vehicle, said second controlmeans constituting altitude responsive control means operable .at apredetermined altitude and subsequent to the operation of said firstcontrol means to activate the rocket propulsion means of said recoverystage rocket, said recovery stage rocket propulsion means operating tocause said recovery stage rocketto travel along a pathsubstantiallyopposite to that followed by said delivery stage #rocket,recovery means carried by saidv recovery stage rocket, said recoverymeans operative to reduce the speed of said recovery stage rocket tofacilitate the delivery of said information gathering means to the areaof the initial launching site, and altitude responsive control meanscar- -ried.by said recovery stage rocket, said altitude responsive Tiedby'said vehicle to automatically launch said recovery stage rocketsubsequent to the activation of said informacontrol means operative at apredetermined altitude over said initial launching site to activate saidrecovery means.

9. A two-stage rocket aerial reconnaissance vehicle for gatheringinformation over a designated target area and returning said informationto the area of an initial launching site, comprising, a vehicle bodyhaving a nose section and a tail section, solid state rocket propulsionmeans secured to said body, a recovery stage rocket in-.

eluding a nose section incorporated within the body of saidreconnaissance vehicle and detachably secured to said reconnaissancevehicle so as to be reversely mounted relative to the direction oftravel of said vehicle, whereby the nose section of said recovery stagerocket is reversely positioned relative to the nose section of saidreconnaissance vehicle, said recovery stage roeket having solid staterocket propulsion means and laterally extending fin members securedthereto, said fin members being mounted exteriorly of said recoverystage rocket and capable of longitudinal movement along the bodythereof, means mounted upon said vehicle to produce a reverse thrust ina direction opposite the direction of travel of said vehicle, programmedcontrol means including altitude responsive control means carried bysaid vehicle, said programmed control means operating over the targetarea to sequentially cause the ejection of the nose section of saidreconnaissance vehicle, initiation of the information gathering cycle ofsaid information gathering means, actuation of said reverse thrustproducing means, and launching of said recovery stage rocket along apath substantially opposite to that followed by said reconnaissancevehicle, recovery means carried by said recovery stage rocket, saidrecovery means operative to reduce the speed of said recovery stagerocket to facilitate the delivery of said information gathering means tothe area of the initial launching site, and altitude responsive controlmeans carried by said recovery stage rocket, said altituderesponsivecontrol means operative at a predetermined altitude over said initiallaunching site to activate said recovery means.

10. A two-stage rocket aerial reconnaissance vehicle for gatheringinformation over a designated target area and returning said informationto the area of an initial launching site, comprising, a delivery stagerocket including a nose section and rocket propulsion means, a recoverystage rocket detachably secured to said delivery stage rocket so as tobe reversely mounted relative to the.

direction of travel of said delivery stage rocket, the forward portionof said recovery stage rocket being reversely positioned relative to thenose section of said delivery stage rocket, rocket propulsion meansmounted upon said recovery stage rocket, first control means carried bysaid vehicle, said first control means operating to initiate theinformation gathering cycle of said informa tion gathering means, secondcontrol means carried by said. vehicle, said second control meansconstituting altitude responsive control means operative at apredetermined altitude subsequent to the operation of said first controlmeans to activate the rocket propulsion means of said recovery stagerocket, said recovery stage rocket propulsion means operating to causesaid recovery stage rocket to travel along a path substantially oppositethat followed by said delivery stage rocket, recovery means carried bysaid recovery stage rocket, said recovery means operative to reduce thespeed of said recovery stage rocket to facilitate the delivery of saidinformation gathering means to the area of the initial launching site,and control means carried by said recovery stage rocket, said controlmeans operative at a predetermined point over said initial launchingsite to activate said recovery means.

11. An aerial reconnaissance vehicle for gathering information over adesignated target area and returning said information to the area of aninitial launching site, comprising a delivery stage rocket including anose section and rocket propulsion means, a recovery stage rocketdetachably secured to said delivery stage missile so as to be reverselymounted relative tothe direction of travel of the said delivery stagerocket, the forward section of said recovery stage rocket beingreversely positioned relative to the nose section of said delivery stagerocket, rocket propulsion means secured to said recovery stage rocket,information gathering means carried by said recovery stage rocket, meansto provide a reverse thrust secured to said recovery stage rocket, saidreverse thrust means operating to provide a thrust in a directionopposite to the direction of travel followed by said delivery stagerocket, programmed control means carried by said vehicle, saidprogrammed control means operating over said target area to activatesaid reverse thrust producing means and initiate the launching of saidrecovery stage rocket along a path substantially opposite to thatfollowed by said delivery stage rocket, recovery means carried by saidrecovery stage rocket, said recovery means operative to reduce the speedof said recovery stage rocket to facilitate the delivery of saidinformation gathering means to the area of the initial launching site,and recovery control means carried by said recovery stage rocket, saidrecovery control means operative over said initial launching site toactuate said recovery means. 7

12. An aerial reconnaissance vehicle for gathering information over adesignated target area and returning said information to the area of aninitial launching site, com

prising, a delivery stage rocket, a recovery stage missile detachablysecured to said delivery stage rocket so as to be reversely mountedrelative to the direction of travel of said delivery stage rocket,information gathering means carried by said recovery stage rocket,control means carried by said vehicle for automatically launching saidrecovery stage rocket over said target area to cause said recovery stagerocket to travel along a path substantially opposite to that followed bysaid delivery stage rocket, recovery means carried by said recoverystage rocket, said recovery means operative to reduce the speed of saidrecovery stage rocket to facilitate the delivery of said informationgathering means to the area of the initial launching site, and recoverycontrol means carried by said recovery stage rocket, said recoverycontrol means operative over said initial launching site to activatesaid recovery means.

13. An aerial reconnaissance vehicle for gathering information over adesignated target area and returning said information to the area of aninitial launching site, comprising, a delivery stage rocket, a recoverystage missile detachably secured to said delivery stage rocket so as tobe reversely mounted relative to the direction of travel of saiddelivery stage rocket, information gathering means carried by.saidrecovery stage rocket, first control means carried by said vehicle forinitiating the information gathering cycle of said information gatheringmeans at a first position over said target area, second control meanscarried by said vehicle, said second control means constituting altituderesponsive control means operative at a predetermined altitudesubsequcnt to the operation of said first control means to launch saidrecovery stage rocket along a path substantially opposite to thatfollowed by said delivery stage rocket, recovery means carried by saidrecovery stage rocket, said recovery means operative to reduce the speedof said recovery stage rocket to facilitate the delivery of saidinformation gathering means to the area of the initial launching site,and altitude responsive control means carried by said recovery stagerocket, said altitude responsive control means operative at apredetermined altitude over said initial launching site to activate saidrecovery means.

14. A method for obtaining aerial intelligence information of apredetermined target area from a position above said area which includeslaunching a twostage rocket from an initial launching site, causing saidrocket to proceed along a course to said target area, automaticallyactivating information gathering equipment carried by the second stageof said rocket above said target area, automatically launching thesecond stage of said rocket from said first stage in a directionopposite to that followed by said first stage subsequent to theactivation of said information gathering equipment, causing said secondstage to carry the information gathering equipment along a return courseto a point above the area of said initial launching site, andautomatically activating a recovery unit to decrease the speed of saidsecond stage to facilitate the recovery of said information gatheringequipment.

15. A method for obtaining aerial intelligence information of apredetermined target area from a position above said area which includeslaunching a two-stage rocket to follow a trajectory to said target area,activating information gathering equipment carried by the second stageof said rocket at a first point above said target area, producing athrust opposite to the direction of travel of said two stage rocket toslow and stabilize the rocket, launching the second stage of said rocketfrom the first stage in a direction opposite to that fol-lowed by saidfirst stage when the rocket reaches a predetermined altitude above saidtarget area, causing said second stage to carry the informationgathering equipment along the return trajectory to the area of saidinitial launching site, and automatically activating a recovery unit ata predetermined point above said initial launching site to decrease thespeed of said second stage and facilitate the recovery of saidinformation gathering equipment.

16. An aerial reconnaissance vehicle forg-athering information over adesignated target area and returning said information to the area of aninitial launching site, comprising, a delivery stage rocket providedwith a nose section and rocket propulsion means, a recovery stage rocketdetachably secured to said delivery stage rocket so as to be reverselymounted relative to the direction of travel of said delivery stagerocket, the central longitudinal axis of said recovery stage rocketbeing positioned in substantial alignment with the central lonigtudinalaxis of said delivery stage rocket, said recovery stage rocket havingrocket propulsion means and laterally extending fin members securedthereto, said fin members being mounted ex teriorly of said recoverystage rocket and being capable of longitudinal movement along the bodythereof, information gathering means carried by said recovery stagerocket, first control means carried by said vehicle, said first controlmeans operating to initiate the information gathering cycle of saidinformation gathering means and to cause the ejection of the nosesection of said delivery stage rocket at a first point over said targetarea, second control means carried by said vehicle, said. second controlmeans constituting altitude responsive control means operable at apredetermined altitude and subsequent to the operation of said firstcontrol means to activate the rocket propulsion means of said recoverystage rocket, said recovery stage rocket propulsion means operating tocause said recovery stage rocket to travel along a path substantiallyopposite to that followed by said delivery stage rocket, recovery meanscarried by said recovery stage rocket, said recovery means operative toreduce the speed of said recovery stage rocket to facilitate thedelivery of said information gathering means to the area of the initiallaunching site, and altitude responsive control means carried by saidrecovery stage rocket, said altitude responsive control means operativeat a predetermined altitude over said initial launching site to activatesaid recovery means.

17. 'An aerial reconnaissance vehicle for gathering information over adesignated target area and returning said information to the area of aninitial launching site, comprising, a delivery stage rocket, a recoverystage rocket detachably secured to said delivery stage rocket so as tobe reversely mounted relative to the direction of travel of saiddelivery stage rocket, the central longitudinal axis of said recoverystage rocket being positioned in substantial alignment with the centrallongitudinal axis of said deliverystage rocket, information gatheringmeans carried by said recovery stage rocket control means carried bysaid vehicle for automatically launching said recovery stage rocket overs-aidtarget area to cause-said recovery stage rocket totravel along apath substantially opposite stage rocket, said recovery control meansoperative over References Cited in the file of this patent said initiallaunching site to activate said recovery means; 10 3,015,456

UNITED STATES PATENTS Goddard July 7, 1914 Anzal one Mar. 28,, I944 Hild'Nov. 2, 1954 Campbell Sept. 6, 1955 Jehn MayS, .1956 C-an'au Sept; 18,1956 Pion May 31 1960 Deisinger Jan 2, 1962

1. AN AERIAL RECONNAISSANCE VEHICLE FOR GATHERING INFORMATION OVER ADESIGNATED TARGET AREA AND RETURNING SAID INFORMATION TO THE AREA OF ANINITIAL LAUNCHING SITE, COMPRISING, A DELIVERY STAGE RACKET INCLUDING AHOLLOW BODY SECTION, A NOSE SECTION, AND A TAIL SECTION, MOUNTING MEANSSECURED WITHIN SAID HOLLOW BODY SECTION, A RECOVERY STAGE ROCKET HAVINGA NOSE SECTION AND A TAIL SECTION, SAID RECOVERY STAGE ROCKET BEINGREVERSELY MOUNTED WITHIN SAID HOLLOW BODY SECTION BY SAID MOUNTINGMEANS, WHEREBY THE NOSE SECTION OF SAID RECOVERY STAGE ROCKET ISPOSITIONED ADJACENT THE TAIL SECTION OF SAID DELIVERY STAGE ROCKET,INFORMATION GATHERING MEANS CARRIED BY SAID RECOVERY STAGE ROCKET,ALTITUDE RESPONSIVE CONTROL MEANS CARRIED BY SAID VEHICLE FOR ACTIVATINGSAID INFORMATION GATHERING MEANS WHEN THE VEHICLE REACHES APREDETERMINED FIRST ALTITUDE OVER SAID TARGET AREA, AND ALTITUDERESPONSIVE LAUNCHING CONTROL MEANS MOUNTED WITHIN SAID VEHICLE TO CAUSETHE LAUNCHING OF SAID RECOVERY STAGE ROCKET FROM THE TAIL SECTION OFSAID DELIVERY STAGE ROCKET SUBSEQUENT TO THE ACTIVATION OF SAIDINFORMATION GATHERING MEANS WHEN SAID VEHICLE REACHES A SECONDPREDETERMINED ALTITUDE OVER SAID TARGET AREA, SAID RECOVERY STAGE ROCKETBEING CAPABLE OF RETURNING SAID INFORMATION GATHERING MEANS TO THE AREAOF SAID INITIAL LAUNCHING SITE UPON DETACHMENT FROM SAID DELIVERY STAGEROCKET.